EP2669474B1 - Transition channel for a fluid flow engine and fluid flow engine - Google Patents
Transition channel for a fluid flow engine and fluid flow engine Download PDFInfo
- Publication number
- EP2669474B1 EP2669474B1 EP12170498.5A EP12170498A EP2669474B1 EP 2669474 B1 EP2669474 B1 EP 2669474B1 EP 12170498 A EP12170498 A EP 12170498A EP 2669474 B1 EP2669474 B1 EP 2669474B1
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- European Patent Office
- Prior art keywords
- flow
- suction
- pressure
- transition duct
- support ribs
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- 239000012530 fluid Substances 0.000 title claims description 22
- 238000002156 mixing Methods 0.000 claims description 18
- 238000007664 blowing Methods 0.000 claims description 8
- 238000011144 upstream manufacturing Methods 0.000 claims description 5
- 238000001816 cooling Methods 0.000 claims 1
- 239000000203 mixture Substances 0.000 description 17
- 206010041662 Splinter Diseases 0.000 description 7
- 230000018109 developmental process Effects 0.000 description 4
- 230000005284 excitation Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
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- 238000013467 fragmentation Methods 0.000 description 2
- 238000006062 fragmentation reaction Methods 0.000 description 2
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/023—Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/10—Two-dimensional
- F05D2250/18—Two-dimensional patterned
- F05D2250/184—Two-dimensional patterned sinusoidal
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the invention relates to a transitional channel for a turbomachine according to the preamble of patent claim 1 and a turbomachine.
- a transition duct in an axial flow machine such as an aircraft engine directs a main flow from an upstream flow cross section to a radially offset flow cross section.
- the transition duct is usually annular in cross-section and is disposed, for example, between a high pressure turbine and a turning turbine turbine (TMTF).
- TMTF turning turbine turbine
- the transition duct may also be arranged between a high-pressure turbine and a medium-pressure turbine and between the medium-pressure turbine and a low-pressure turbine.
- a transition duct may conduct the flow in an analogous manner from an upstream to a downstream flow cross section and be arranged, for example, between a low-pressure compressor and a high-pressure compressor.
- a transition channel generally has similar, circumferentially distributed support ribs.
- the support ribs also cause a deflection of the flow, in particular in the circumferential direction, to improve a flow to the first blade row of the downstream turbine or a compressor stage.
- the support ribs usually have a large relative thickness, ie a ratio of profile thickness to chord length, and / or a small blade height ratio, ie a ratio of blade height to chord length.
- the comparatively large relative thickness or small relative height of the support ribs may be required in particular for static reasons.
- such a geometry of the support ribs leads to strong secondary flows. It creates edge areas with turbulent flow, which can dominate the flow field. Such secondary flows adversely affect the flow of subsequent blades. In particular, they can limit a maximum possible deflection at hub and housing and lead to energy transfer losses.
- the secondary flows can lead to suggestions of the first blade row of the downstream turbine and thus to a high noise level.
- a gas turbine having an annular transition duct extending from a high pressure turbine to a low pressure turbine is known.
- the transition channel has a radially inner channel wall and a radially outer channel wall, between which circumferentially distributed vanes are arranged, each having a wing profile for deflecting a flow from an entrance surface to an exit surface of the transition channel.
- the inner circumferential surface has a particular curvature.
- FIG US 2009 324400 A1 A channel within a turbine exhaust housing having support ribs having passageways through which a portion of the gas channel fluid flows due to a pressure difference between leading and trailing edges is shown in FIG US 2009 324400 A1 known.
- a transition duct with vanes of different profile thickness is from the US Pat. No. 3,704,075 known.
- a turbine ring is out of the US 20100209238A1 known.
- the object of the invention is to provide a transitional channel for a turbomachine, which eliminates the aforementioned disadvantages and allows improved follow-up mixing. Furthermore, it is an object of the invention to provide a turbomachine with a high efficiency and low noise.
- a transition duct according to the invention for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section has support ribs extending between a radially inner duct wall and a radially outer duct wall and a profile for deflecting a flow from an entry surface have to an exit surface of the transition channel.
- the support ribs each have a profile variation in the region of their trailing edge and / or at least one blow-out opening for blowing out a fluid.
- the profile variation and / or the at least one blow-out opening cause passive and / or active wake-up mixing of the outflow, resulting in rapid flow calming.
- the inflow of rotor blades downstream of the exit surface of the transition channel is improved so that energy transfer losses and aerodynamic excitations of the rotor blades are minimized.
- a suction-side partial flow and a partial flow on the pressure side are equalized with respect to their outflow velocity, whereby vortices during the merging of the partial flows are reduced behind the trailing edge, which leads to an early-calmed wake flow.
- the at least one exhaust opening or active follow-up mixing By means of the at least one exhaust opening or active follow-up mixing, energization of the outflow takes place by blowing in a fluid, which likewise improves after-run mixing.
- the support ribs are cooled by the fluid in the area of their trailing edge, which reduces their thermal load.
- the trailing edge is alternately offset to the suction side and the pressure side.
- the trailing edge has a lateral or circumferentially extending waveform with a plurality of wave crests and troughs, whereby the trailing edge is increased and thus a suction-side and a pressure-side partial flow are quasi fanned out.
- the partial flows are considered by the waveform in the radial direction sections overlaid alternately, so that not only a "lateral" mixing, but also a "radial” mixing takes place.
- the waveform is uniform and such that the wave crests and troughs have the same suction side and pressure side extensions.
- the trailing edge is formed like a wave in the flow direction.
- a plurality of profile shortenings (wave troughs) and profile extensions (wave crests) are created, whereby the suction-side partial flow and the pressure-side partial flow in each case in sections earlier in time (wave trough) or temporally later (wave crest) flow away from the trailing edge.
- a mixing zone is partially advanced (troughs) in sections, thus introducing mixing at an early stage.
- the waveform is uniform.
- the at least one blow-off opening emerges from the rear edge between the suction side and the pressure side.
- the at least one exhaust opening is arranged on the skeleton line of the support rib and the fluid is blown evenly between the outflowing partial flows, so that a deflection of the suction or the pressure-side partial flow is prevented in the circumferential direction.
- the at least one exhaust opening is preferably formed as a longitudinal slot which extends from the inner channel wall to the outer channel wall. Furthermore, at this variant, a suction-side slot surface wavy and a pressure-side slot surface formed without variation. As a result, the suction-side slot surface is enlarged relative to the pressure-side slot surface. In addition, the fluid flow is fanned out by the waveform suction side quasi.
- a suction-side outflow surface opposed to the suction-side slot surface can be designed to be corrugated.
- the suction-side slot surface is provided with a profile variation, so that in combination with the at least one blow-out opening, both passive and active wake-up mixing takes place.
- a pressure-side slit surface is undulating and an opposite suction-side slit surface is randomly shaped.
- the pressure-side slot surface is enlarged relative to the suction-side slot surface.
- the fluid flow is fanned out by the pressure side of the waveform.
- a pressure-side outflow surface opposite the pressure-side slot surface may be wave-shaped, so that in combination with the at least one exhaust opening, both passive and active follow-up mixing takes place.
- the at least one exhaust opening emerges on the suction side from the profile.
- the at least one exhaust opening may be formed as a slot, as a plurality of slots or as a plurality of bore-like openings.
- the orientation of the at least one exhaust opening and the shape of a downstream trailing edge section is preferably such that the so-called "Coanda effect" can form. That is, the fluid flow follows after detachment from the trailing edge portion of its outer contour, so that on the one hand is energized by the blowing quasi only a near-profile boundary layer and on the other hand no cross flows are introduced into the profilfemen layers of the suction side partial flow.
- At least one flow divider blade which has a smaller relative profile thickness than the support ribs, can be arranged between the support ribs.
- the at least one flow divider blade is based on the knowledge that turbulences, flow losses and / or deflection restrictions can be reduced if additional deflection elements are arranged between the support ribs also profiled for deflecting the flow, which form a slimmer and / or shortened flow divider in comparison with the support ribs are.
- the flow divider vanes in the region of their trailing edge are also provided with a profile variation and / or with at least one blow-off opening, so that a passive and / or an active follow-up mixing of the respective flow divider vanes side outflow takes place.
- a preferred turbomachine has a transition channel according to the invention. Due to the rapid after-run mixing, this causes an improved inflow of rotor blades downstream of the exit surface of the transition duct. The improved inflow results in minimized energy transmission losses and thus in a high efficiency as well as in a minimized aerodynamic excitation of the subsequent rotor blades and thus in a noise reduction in comparison to turbomachines with a conventional transition duct.
- the transition channel is preferably arranged on the turbine side, but may also be arranged on the compressor side.
- FIG. 1 is an example of a transition channel 1 between a high-pressure turbine 2 and a Low-pressure turbine 4 of an axial flow machine such as an aircraft engine in the axial half or meridian section (upper part of the figure) and in a plane development or in profile section (lower part of the figure).
- the transition duct 1 is fixedly mounted in a turbine housing, whereas the high-pressure turbine 2 and the low-pressure turbine 4 each have blade row 6, which rotate about a rotation axis or turbine axis R in the direction of rotation U.
- the transitional channel 1 surrounds the axis of rotation R and has an annular flow cross-section. It has a radially inner channel wall 8, a radially outer channel wall 10 and a high-pressure turbine-side inlet surface F 1 and a low-pressure turbine-side outlet surface F2.
- the entrance surface F 1 is arranged radially inwardly of the exit surface F 2 , so that a flow passing through the transition channel 1 12 is guided radially obliquely with respect to the axis of rotation R to the outside.
- the flow angle ⁇ 1 indicates a deflection angle of an inlet flow 12 'in the transition channel 1 to the axis of rotation R.
- the flow angle ⁇ 2 indicates a deflection angle of an exit flow 12 "from the transition channel 1 to the rotation axis R.
- the transitional channel 1 has a plurality of support ribs 14 for stiffening, which extend between the inner channel wall 8 and the outer channel wall 10 and which are distributed uniformly in the transition channel 1 viewed in the circumferential direction.
- the support ribs 14 have a comparatively large relative thickness in order to fulfill their supporting effect and to be able to pick up supply lines which are not outlined.
- they have a wing-like profile for deflecting the flow 12 in the circumferential direction or rotation direction.
- they In the region of their respective trailing edge 16, they have a follow-up mixture indicated by a circle 18 in the form of a passive tracking mixture 20, ( FIGS. 2 and 3 ), in the form of at least one active tailing mixture 22 ( FIGS. 4 . 5 and 8th ) or in the form of a combined active and passive follow-up mixture 18, 20 ( FIGS. 6 and 7 ).
- FIG. 2 An in FIG. 2 exemplary passive tracking mix shown is a trailing edge profile variation 20, which is formed alternately to the suction side 24 and the opposite pressure side 26.
- the profile variation 20 thus has a waveform that is preferably uniform.
- the trailing edge 16 has a multiplicity of lateral wave crests and wave troughs, by means of which, on the one hand, the suction side 24 and the pressure side 26 are enlarged in area in the trailing edge region.
- a respective suction-side partial flow and a partial flow on the pressure side in the region of the trailing edge 16 are fanned out laterally or in the circumferential direction and are alternately guided over one another in sections in the radial direction.
- the trailing edge 16 is axially offset from a conventional rectilinear trailing edge.
- FIG. 3 Exemplary passive tracking mixture shown is a trailing edge profile variation 20, which is wavy viewed in the flow direction.
- the respective suction-side partial flow and the pressure-side partial flow is fanned out in the radial direction, wherein due to the created by the wave peaks and the troughs local profile extensions or profile shortening the suction and pressure side streams partially later in time (wave mountain) or earlier (wave trough) of the jeweilegen support rib 14 flow, so that the merger of the partial flows in the axial direction or viewed in the flow direction over a direction indicated by dashed auxiliary line 27 conventional trailing edge is advanced in time.
- the waveform is uniform.
- the support ribs 14 each have an exhaust opening 22 for blowing out a fluid in the region of their trailing edges 16.
- the blow-out opening 22 is formed as a longitudinal slot extending from the inner channel wall 8 to the outer channel wall 10 (s. Fig. 1 ).
- the longitudinal slot 22 lies on the skeleton line of the support rib 14 and thus bisects the trailing edge 16 into a suction side section 28 and a pressure side portion 30.
- the suction side portion 28 has a suction side slit surface 32 delimiting the blowout port 22 and the pressure side portion 28 has an opposite pressure side slit surface 34 for confining the blowout port 22.
- the suction side slit surface 32 is undulatingly provided with a plurality of wave crests and troughs.
- the pressure-side slot surface 34 is random and straight in the section shown.
- a suction-side outflow surface 36 of the suction-side section 28 opposite the suction-side slit surface 32 and a pressure-side outflow surface 38 of the pressure-side section 30 opposite the pressure-side slit surface 34 are likewise formed without a contour variation.
- suction and pressure-side partial flows are brought together after the flow around the profile behind the trailing edge 16, wherein a flow of fluid between the partial flows is blown through the Ausblasöf Anlagen 22, the side fanned out by the wavy inner contour of the suction side slot surface 32 of the fluid flow on one side, namely the suction side becomes.
- FIG. 5 is a further example of an active tracking mixture in the region of a trailing edge 16 of the support ribs 14 shown.
- a pressure-side slit surface 34 is wave-shaped and a suction-side slit surface 32 is random.
- the rear edge 16 forming surfaces such as a suction-side outflow surface 36 and a pressure-side outflow surface 38 are also formed in this embodiment without a contour variation.
- suction and pressure-side partial flows are brought together after the flow around the profile behind the trailing edge 16, wherein through the Ausblasöf Anlagen 22, a fluid flow is blown between the partial streams, the side fanned out by the wavy inner contour of the pressure side slot surface 34 of the fluid flow on one side, on the pressure side becomes.
- FIG. 6 an example of a combined active and passive and thus a hybrid wake-up mixture 20, 22 is shown.
- the suction-side outflow surface 36 is provided with a profile variation 20, and thus not only a suction-side slit surface 32.
- the profile variation 20 is also undulating with a plurality of wave crests and troughs.
- the pressure-side outflow surface 38 of the pressure side section 30 is without a contour variation educated.
- a suction-side partial flow is laterally fanned out laterally.
- the positioning of the inner contouring and the profile variation 20 relative to one another is preferably such that a wave peak of the profile variation 20 is arranged in the region of a wave trough of the inner contouring and vice versa.
- the profile variation 20 and the inner contouring are identical.
- FIG. 7 is shown another example of a combined active and passive, and thus a hybrid wake-up mixture 20, 22.
- the pressure-side outflow surface 38 is provided with a profile variation 20 and thus not only a pressure-side slot surface 34.
- the profile variation 20 is also wave-shaped provided with a plurality of wave crests and wave troughs.
- the suction-side outflow surface 36 of the suction side section 28 is formed without a contour variation.
- a pressure-side partial flow is fanned out laterally passively.
- the positioning of the inner contouring and the profile variation 20 relative to one another is preferably such that a wave peak of the profile variation 20 is arranged in the region of a wave trough of the inner contouring and vice versa.
- the profile variation 20 and the inner contouring are identical.
- FIG. 8 an example of an active wake-up mixture is shown, in which the so-called "Coanda effect" is exploited.
- the support ribs 14 are provided in the region of their trailing edges 16 with in each case at least one suction-side discharge opening 22 for blowing out a fluid into a profile-near boundary layer.
- the blow-out opening 22 is formed as a longitudinal slot or as a plurality of holes. It divides the suction side 24 into a front suction side section 40 and into a rear suction side section 28.
- a pressure side section 30 has an unvaried outflow surface 38 and is bulged toward the suction side 24 in such a way that its extension forms the suction side section 28 with a concave suction-side outflow surface 36.
- the outflow surface 36 has such an outer contour that the outflow of the outlet opening 22 fluid after detachment from the outflow surface 34 of the outer contour follows a near profile area and thus cross flows are avoided in profilfeme partial flow layers.
- flow divider blades 20 may be disposed in a downstream portion of the overchannel 1.
- the splitter blades 20 can individually ( FIG. 9 ) or multiple times ( FIG. 10 ) are arranged between the support ribs 14 and also provided with an active and / or passive follow-up mixture 18 in the region of their trailing edges 16.
- the splinter blades 42 cause a flow division between the support ribs 14 and contribute to the deflection of the flow 12 in the circumferential direction.
- the splitter blades 42 are shorter than the support ribs 14 and have an airfoil profile which is significantly slimmer than the profile of the support ribs 14.
- three-dimensional parasitic secondary currents 44 can form in the rear region of the transitional channel 1. These secondary flows 44 are induced by the double deflection, namely the deflection radially outwards on the one hand and the deflection in the circumferential direction on the other hand, as well as the complex velocity profile of the flow 12.
- the secondary flows 22 can lead to an unfavorable flow of the first rotor blades 6 of the low-pressure turbine 4 and to an excitation of the rotor blades 6.
- the arrangement of the slender splitter blades 42 between the thicker support ribs 14, the generation of the parasitic secondary flows 42 can be significantly reduced.
- FIG. 10 the arrangement of two splitter vanes 42a, 42b between adjacent support ribs 18 is shown. It is desirable that the highest possible proportion of the flow deflection is taken over by the splitter blades 42 (42a, 42b).
- the number of long and heavy support ribs 14 is determined essentially by the stability requirements and the number or cross-sectional size of the supply lines to be received in the support ribs 14.
- up to five splitter blades 42 can be arranged between two support ribs 14.
- FIG. 10 geometric sizes of the support ribs 14 and the splitter blades 42a, 42b indicated.
- An axial depth of the support ribs 14 is indicated with L ax , a profile viewing length with L and a maximum profile thickness with D max .
- the corresponding nomenclatures are transferable to the splitter blades 42a, 42b by the additional index "splitter”.
- An axial length or depth of the transition channel 1 itself can be indicated by L ax, TMTF .
- the axial depth L ax, TMTF of the transition channel 1 may coincide or be defined with the axial length or depth L ax of the support ribs 14.
- a transitional channel for a turbomachine for forming a flow channel between an upstream flow cross-section and a downstream flow cross-section, with support ribs extending between a radially inner channel wall and a radially outer channel wall and a profile for deflecting a flow of an inlet surface to an outlet surface of the transition channel, wherein the support ribs each have a profile variation and / or at least one exhaust opening for blowing out a fluid in the region of its trailing edge, as well as a turbomachine with such a transitional channel.
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Description
Die Erfindung betrifft einen Übergangskanal für eine Strömungsmaschine nach dem Oberbegriff des Patentanspruchs 1 sowie eine Strömungsmaschine.The invention relates to a transitional channel for a turbomachine according to the preamble of
Ein Übergangs- bzw. Umlenkkanal in einer axialen Strömungsmaschine wie ein Flugzeugtriebwerk leitet eine Hauptströmung von einem stromaufwärtigen Strömungsquerschnitt zu einem radial versetzten Strömungsquerschnitt. Der Übergangskanal hat gewöhnlich einen ringförmigen Querschnitt und ist bspw. zwischen einer Hochdruckturbine und einer Niederdruckturbine (Turning Mid Turbine Frame, TMTF) angeordnet. Bei einer dreiteiligen Auslegung einer Turbine kann der Übergangskanal auch zwischen einer Hochdruckturbine und einer Mitteldruckturbine sowie zwischen der Mitteldruckturbine und einer Niederdruckturbine angeordnet sein. Bei Verdichtem kann ein Übergangskanal die Strömung in analoger Weise von einem stromaufwärtigen zu einem stromabwärtigen Strömungsquerschnitt leiten und bspw. zwischen einem Niederdruckverdichter und einem Hochdruckverdichter angeordnet sein.A transition duct in an axial flow machine such as an aircraft engine directs a main flow from an upstream flow cross section to a radially offset flow cross section. The transition duct is usually annular in cross-section and is disposed, for example, between a high pressure turbine and a turning turbine turbine (TMTF). In a three-part design of a turbine, the transition duct may also be arranged between a high-pressure turbine and a medium-pressure turbine and between the medium-pressure turbine and a low-pressure turbine. In the case of compressors, a transition duct may conduct the flow in an analogous manner from an upstream to a downstream flow cross section and be arranged, for example, between a low-pressure compressor and a high-pressure compressor.
Zur Versteifung weist ein Übergangskanal im Allgemeinen gleichartige, über den Umfang verteilte Stützrippen auf. Die Stützrippen bewirken zudem eine Umlenkung der Strömung, insbesondere in Umfangsrichtung, um eine Anströmung zur ersten Laufschaufelreihe der stromabwärtigen Turbine bzw. einer Verdichterstufe zu verbessern.For stiffening, a transition channel generally has similar, circumferentially distributed support ribs. The support ribs also cause a deflection of the flow, in particular in the circumferential direction, to improve a flow to the first blade row of the downstream turbine or a compressor stage.
Die Stützrippen haben üblicherweise eine große relative Dicke, d.h. ein Verhältnis von Profildicke zu Sehnenlänge, und/oder ein kleines Schaufelhöhenverhältnis, d.h. ein Verhältnis von Schaufelhöhe zu Sehnenlänge. Die vergleichsweise große relative Dicke bzw. kleine relative Höhe der Stützrippen kann insbesondere aus statischen Gründen erforderlich sein. Eine solche Geometrie der Stützrippen führt jedoch zu starken Sekundärströmungen. Es entstehen Randbereiche mit verwirbelter Strömung, welche das Strömungsfeld dominieren können. Derartige Sekundärströmungen beeinflussen die Anströmung von nachfolgenden Schaufeln nachteilig. Sie können insbesondere eine maximal mögliche Umlenkung an Nabe und Gehäuse begrenzen und zu Energieübertragungsverlusten führen. Zudem können die Sekundärströmungen zu Anregungen der ersten Laufschaufelreihe der stromabwärtigen Turbine und somit zu einer hohen Geräuschentwicklung führen. Darüber hinaus können die im Vergleich zu konventionellen Statorgeometrien deutlich geringeren Schaufelzahlen der Übergangskanäle aerodynamische Anregungen der nachfolgenden Rotorschaufeln mit fundamentalen Moden, so genannten "Engine Orders", im Arbeitsbereich der Strömungsmaschine bewirken.The support ribs usually have a large relative thickness, ie a ratio of profile thickness to chord length, and / or a small blade height ratio, ie a ratio of blade height to chord length. The comparatively large relative thickness or small relative height of the support ribs may be required in particular for static reasons. However, such a geometry of the support ribs leads to strong secondary flows. It creates edge areas with turbulent flow, which can dominate the flow field. Such secondary flows adversely affect the flow of subsequent blades. In particular, they can limit a maximum possible deflection at hub and housing and lead to energy transfer losses. In addition, the secondary flows can lead to suggestions of the first blade row of the downstream turbine and thus to a high noise level. In addition, compared to conventional stator geometries significantly lower blade numbers of the transitional channels aerodynamic excitations of the subsequent rotor blades with fundamental modes, so-called "engine orders" effect in the workspace of the turbomachine.
Aus der
Ein Kanal innerhalb eines Turbinenaustrittsgehäuses mit Stützrippen, die Durchgangskanäle aufweisen, durch welche ein Teil des Gaskanalfluids aufgrund einer Druckdifferenz zwischen Vorder- und Hinterkante strömt, ist aus der
Ein Übergangskanal mit Leitschaufeln unterschiedlicher Profildicke ist aus der
Ein Turbinenring ist aus der
Aus der
Aufgabe der Erfindung ist es, einen Übergangskanal für eine Strömungsmaschine zu schaffen, der die vorgenannten Nachteile beseitigt und eine verbesserte Nachlaufausmischung ermöglicht. Des Weiteren ist es Aufgabe der Erfindung, eine Strömungsmaschine mit einem hohen Wirkungsgrad und mit einer geringen Geräuschentwicklung zu schaffen.The object of the invention is to provide a transitional channel for a turbomachine, which eliminates the aforementioned disadvantages and allows improved follow-up mixing. Furthermore, it is an object of the invention to provide a turbomachine with a high efficiency and low noise.
Diese Aufgabe wird gelöst durch einen Übergangskanal mit den Merkmalen des Patentanspruchs 1 und durch eine Strömungsmaschine mit den Merkmalen des Patentanspruchs 12.This object is achieved by a transition channel having the features of
Ein erfindungsgemäßer Übergangskanal für eine Strömungsmaschine, insbesondere ein Flugzeugtriebwerk, zum Bilden eines Strömungskanals zwischen einem stromaufwärtigen Strömungsquerschnitt und einem stromabwärtigen Strömungsquerschnitt hat Stützrippen, die sich zwischen einer radial inneren Kanalwandung und einer radial äußeren Kanalwandung erstrecken und jeweils ein Profil zur Umlenkung einer Strömung von einer Eintrittsfläche zu einer Austrittsfläche des Übergangskanals aufweisen. Erfindungsgemäß haben die Stützrippen jeweils im Bereich ihrer Hinterkante eine Profilvariation und/oder zumindest eine Ausblasöffnung zum Ausblasen eines Fluids.A transition duct according to the invention for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross section and a downstream flow cross section has support ribs extending between a radially inner duct wall and a radially outer duct wall and a profile for deflecting a flow from an entry surface have to an exit surface of the transition channel. According to the invention, the support ribs each have a profile variation in the region of their trailing edge and / or at least one blow-out opening for blowing out a fluid.
Die Profilvariation und/oder die zumindest eine Ausblasöffnung bewirken eine passive und/oder eine aktive Nachlaufausmischung der Abströmung, wodurch eine schnelle Strömungsberuhigung erfolgt. Als Ergebnis der frühzeitigen Nachlaufausmischung wird die Zuströmung von Rotorschaufeln stromabwärts der Austrittsfläche des Übergangskanals verbessert, so dass Energieübertragungsverluste und aerodynamische Anregungen der Rotorschaufeln minimiert werden. Mittels der Profilvariation bzw. passiven Nachlaufausmischung werden ein saugseitiger Teilstrom und ein druckseitiger Teilstrom bezüglich ihrer Abströmgeschwindigkeit vergleichmäßigt, wodurch Wirbel beim Zusammenführen der Teilströme hinter der Hinterkante reduziert werden, was zu einer frühzeitig beruhigten Nachlaufströmung führt. Mittels der zumindest einen Ausblasöffnung bzw. aktiven Nachlaufausmischung erfolgt eine Energetisierung der Abströmung durch Einblasen eines Fluids, wodurch ebenfalls die Nachlaufausmischung verbessert wird. Zudem werden die Stützrippen durch das Fluid im Bereich Ihrer Hinterkante gekühlt, wodurch deren thermische Belastung reduziert wird. Bei einer Kombination der passiven und der aktiven Nachlaufausmischung zu einer hybridartigen Nachlaufausmischung erfolgt sowohl eine Vergleichmäßigung als auch eine Energetisierung der Abtrömung.The profile variation and / or the at least one blow-out opening cause passive and / or active wake-up mixing of the outflow, resulting in rapid flow calming. As a result of the early post-mix, the inflow of rotor blades downstream of the exit surface of the transition channel is improved so that energy transfer losses and aerodynamic excitations of the rotor blades are minimized. By means of the profile variation or passive follow-up mixing, a suction-side partial flow and a partial flow on the pressure side are equalized with respect to their outflow velocity, whereby vortices during the merging of the partial flows are reduced behind the trailing edge, which leads to an early-calmed wake flow. By means of the at least one exhaust opening or active follow-up mixing, energization of the outflow takes place by blowing in a fluid, which likewise improves after-run mixing. In addition, the support ribs are cooled by the fluid in the area of their trailing edge, which reduces their thermal load. For a combination of passive and active Follow-up blending into a hybrid type after-run blending is both equalization and energization of the effluent.
Bei einem Ausführungsbeispiel einer Profilvariation ist die Hinterkante abwechselnd zur Saugseite und zur Druckseite versetzt. Hierdurch hat die Hinterkante eine seitliche bzw. sich in Umfangsrichtung erstreckende Wellenform mit einer Vielzahl von Wellenbergen und Wellentälern, wodurch die Hinterkante vergrößert wird und somit ein saugseitiger und ein druckseitiger Teilstrom quasi aufgefächert werden. Zudem werden die Teilströme durch die Wellenform in radialer Richtung betrachtet abschnittsweise abwechselnd übereinander geführt, so dass nicht nur eine "seitliche" Vermischung, sondern auch eine "radiale" Vermischung erfolgt. Bevorzugterweise ist die Wellenform gleichmäßig ausgebildet und derart, dass die Wellenberge und die Wellentäler die gleichen saugseitigen und druckseitigen Erstreckungen haben.In one embodiment of a profile variation, the trailing edge is alternately offset to the suction side and the pressure side. In this way, the trailing edge has a lateral or circumferentially extending waveform with a plurality of wave crests and troughs, whereby the trailing edge is increased and thus a suction-side and a pressure-side partial flow are quasi fanned out. In addition, the partial flows are considered by the waveform in the radial direction sections overlaid alternately, so that not only a "lateral" mixing, but also a "radial" mixing takes place. Preferably, the waveform is uniform and such that the wave crests and troughs have the same suction side and pressure side extensions.
Bei einem alternativen Ausführungsbeispiel der Profilvariation ist die Hinterkante in Strömungsrichtung betrachtet wellenartig ausgebildet. Hierdurch werden eine Vielzahl von Profilverkürzungen (Wellentäler) und Profilverlängerungen (Wellenberge) geschaffen, wodurch der saugseitige Teilstrom und der druckseitige Teilstrom im Vergleich zu einer herkömmlichen Hinterkante jeweils abschnittsweise zeitlich früher (Wellental) oder zeitlich später (Wellenberg) von der Hinterkante abströmen. Hierdurch wird eine Mischzone abschnittsweise quasi vorverlegt (Wellentäler) und somit eine Vermischung frühzeitig eingeleitet. Bevorzugterweise ist die Wellenform gleichmäßig ausgebildet.In an alternative embodiment of the profile variation, the trailing edge is formed like a wave in the flow direction. As a result, a plurality of profile shortenings (wave troughs) and profile extensions (wave crests) are created, whereby the suction-side partial flow and the pressure-side partial flow in each case in sections earlier in time (wave trough) or temporally later (wave crest) flow away from the trailing edge. As a result, a mixing zone is partially advanced (troughs) in sections, thus introducing mixing at an early stage. Preferably, the waveform is uniform.
Bei einem Ausführungsbeispiel einer aktiven Nachlaufausmischung tritt die zumindest eine Ausblasöffnung zwischen der Saugseite und der Druckseite aus der Hinterkante aus. Durch diese Maßnahme ist die zumindest eine Ausblasöffnung quasi auf der Skelettlinie der Stützrippe angeordnet und das Fluid wird gleichmäßig zwischen die abströmenden Teilströme eingeblasen, so dass eine Ablenkung des saug- oder des druckseitigen Teilstroms in Umfangsrichtung verhindert wird.In one exemplary embodiment of an active follow-up mix, the at least one blow-off opening emerges from the rear edge between the suction side and the pressure side. By this measure, the at least one exhaust opening is arranged on the skeleton line of the support rib and the fluid is blown evenly between the outflowing partial flows, so that a deflection of the suction or the pressure-side partial flow is prevented in the circumferential direction.
Die zumindest eine Ausblasöffnung ist bevorzugterweise als ein Längsschlitz ausgebildet, der sich von der inneren Kanalwandung zur äußeren Kanalwandung erstreckt. Des Weiteren ist bei dieser Variante eine saugseitige Schlitzfläche wellenförmig und eine druckseitige Schlitzfläche variationslos ausgebildet. Hierdurch ist die saugseitige Schlitzfläche gegenüber der druckseitigen Schlitzfläche vergrößert. Zudem wird der Fluidstrom durch die Wellenform saugseitig quasi aufgefächert.The at least one exhaust opening is preferably formed as a longitudinal slot which extends from the inner channel wall to the outer channel wall. Furthermore, at this variant, a suction-side slot surface wavy and a pressure-side slot surface formed without variation. As a result, the suction-side slot surface is enlarged relative to the pressure-side slot surface. In addition, the fluid flow is fanned out by the waveform suction side quasi.
Ergänzend kann eine zur saugseitigen Schlitzfläche entgegengesetzte saugseitige Abströmfläche wellenförmig ausgebildet sein. Hierdurch ist die saugseitige Schlitzfläche mit einer Profilvariation versehen, so dass in Kombination mit der zumindest einen Ausblasöffnung sowohl eine passive als auch eine aktive Nachlaufausmischung erfolgt.In addition, a suction-side outflow surface opposed to the suction-side slot surface can be designed to be corrugated. As a result, the suction-side slot surface is provided with a profile variation, so that in combination with the at least one blow-out opening, both passive and active wake-up mixing takes place.
Bei einem Ausführungsbeispiel, bei dem die zumindest eine Ausblasöffnung als ein Längsschlitz ausgebildet ist, der sich von der inneren Kanalwandung zur äußeren Kanalwandung erstreckt, ist eine druckseitige Schlitzfläche wellenförmig und eine gegenüberliegende saugseitige Schlitzfläche variationslos ausgebildet. Hierdurch ist die druckseitige Schlitzfläche gegenüber der saugseitigen Schlitzfläche vergrößert. Zudem wird der Fluidstrom durch die Wellenform druckseitig quasi aufgefächert.In an embodiment in which the at least one exhaust port is formed as a longitudinal slot extending from the inner duct wall to the outer duct wall, a pressure-side slit surface is undulating and an opposite suction-side slit surface is randomly shaped. As a result, the pressure-side slot surface is enlarged relative to the suction-side slot surface. In addition, the fluid flow is fanned out by the pressure side of the waveform.
Ergänzend kann eine zur druckseitigen Schlitzfläche entgegengesetzte druckseitige Abströmfläche wellenförmig ausgebildet sein, so dass in Kombination mit der zumindest einen Ausblasöffnung sowohl eine passive als auch eine aktive Nachlaufausmischung erfolgt.In addition, a pressure-side outflow surface opposite the pressure-side slot surface may be wave-shaped, so that in combination with the at least one exhaust opening, both passive and active follow-up mixing takes place.
Bei einem Ausführungsbeispiel tritt die zumindest eine Ausblasöffnung saugseitig aus dem Profil aus. Die zumindest eine Ausblasöffnung kann dabei als ein Schlitz, als eine Vielzahl von Schlitzen oder aber als eine Vielzahl von bohrungsartigen Öffnungen ausgebildet sein. Die Ausrichtung der zumindest einen Ausblasöffnung und die Form eines stromabwärtigen Hinterkantenabschnitts ist dabei bevorzugterweise derart, dass sich der sogenannte "Coanda-Effekt" ausbilden kann. D.h. der Fluidstrom folgt nach Ablösung von dem Hinterkantenabschnitt dessen Außenkontur, so dass zum einen durch die Ausblasung quasi nur eine profilnahe Grenzschicht energetisiert wird und zum anderen keine Querströmungen in die profilfemen Schichten des saugseitigen Teilstroms eingebracht werden.In one embodiment, the at least one exhaust opening emerges on the suction side from the profile. The at least one exhaust opening may be formed as a slot, as a plurality of slots or as a plurality of bore-like openings. The orientation of the at least one exhaust opening and the shape of a downstream trailing edge section is preferably such that the so-called "Coanda effect" can form. That is, the fluid flow follows after detachment from the trailing edge portion of its outer contour, so that on the one hand is energized by the blowing quasi only a near-profile boundary layer and on the other hand no cross flows are introduced into the profilfemen layers of the suction side partial flow.
Zwischen den Stützrippen kann zumindest eine Strömungsteilerschaufel angeordnet sein, die eine geringere relative Profildicke als die Stützrippen aufweist. Der zumindest einen Strömungsteilerschaufel liegt die Erkenntnis zugrunde, dass Verwirbelungen, Strömungsverluste und/oder Umlenkungseinschränkungen reduziert werden können, wenn zusätzliche Umlenkelemente zwischen den ebenfalls zur Umlenkung der Strömung profilierten Stützrippen angeordnet sind, die im Vergleich mit den Stützrippen als schlankere und/oder verkürzte Strömungsteiler ausgebildet sind.At least one flow divider blade, which has a smaller relative profile thickness than the support ribs, can be arranged between the support ribs. The at least one flow divider blade is based on the knowledge that turbulences, flow losses and / or deflection restrictions can be reduced if additional deflection elements are arranged between the support ribs also profiled for deflecting the flow, which form a slimmer and / or shortened flow divider in comparison with the support ribs are.
Bevorzugterweise sind die Strömungsteilerschaufeln im Bereich ihrer Hinterkante ebenfalls mit einer Profilvariation und/oder mit zumindest einer Ausblasöffnung versehen, so dass auch eine passive und/oder eine aktive Nachlaufausmischung der jeweiligen strömungsteilerschaufelseitigen Abströmung erfolgt.Preferably, the flow divider vanes in the region of their trailing edge are also provided with a profile variation and / or with at least one blow-off opening, so that a passive and / or an active follow-up mixing of the respective flow divider vanes side outflow takes place.
Eine bevorzugte Strömungsmaschine hat einen erfindungsgemäßen Übergangskanal. Dieser bewirkt aufgrund der schnellen Nachlaufausmischung eine verbesserte Zuströmung von Rotorschaufeln stromabwärts der Austrittsfläche des Übergangskanals. Die verbesserte Zuströmung resultiert in minimierten Energieübertragungsverlusten und somit in einem hohen Wirkungsgrad sowie in einer minimierten aerodynamischen Anregung der nachfolgenden Rotorschaufeln und somit in einer Geräuschreduzierung im Vergleich zu Strömungsmaschinen mit einem herkömmlichen Übergangskanal. Der Übergangskanal ist bevorzugterweise turbinenseitig angeordnet, kann jedoch auch verdichterseitig angeordnet sein.A preferred turbomachine has a transition channel according to the invention. Due to the rapid after-run mixing, this causes an improved inflow of rotor blades downstream of the exit surface of the transition duct. The improved inflow results in minimized energy transmission losses and thus in a high efficiency as well as in a minimized aerodynamic excitation of the subsequent rotor blades and thus in a noise reduction in comparison to turbomachines with a conventional transition duct. The transition channel is preferably arranged on the turbine side, but may also be arranged on the compressor side.
Sonstige vorteilhafte Ausführungsbeispiele der Erfindung sind Gegenstand weiterer Unteransprüche.Other advantageous embodiments of the invention are the subject of further subclaims.
Im Folgenden werden bevorzugte Ausführungsbeispiele der Erfindung anhand stark vereinfachter schematischer Darstellungen näher erläutert. Es zeigen:
Figur 1- eine axiale Schnittansicht und eine teilweise Abwicklung eines Übergangskanals nach einem Ausführungsbeispiel der Erfindung,
Figur 2- eine perspektivische Darstellung einer Stützrippe mit einer beispielhaften hinterkantenseitigen passiven Nachlaufauschmischung,
- Figur 3
- eine Seitenansicht einer Stützrippe mit einer weiteren beispielhaften hinterkantenseitigen passiven Nachlaufauschmischung,
- Figur 4
- eine rückwärtige Darstellung einer Stützrippe mit einer beispielhaften aktiven Nachlaufauschmischung,
- Figur 5
- eine rückwärtige Darstellung einer Stützrippe mit einer weiteren beispielhaften aktiven Nachlaufauschmischung,
Figur 6- eine rückwärtige Darstellung einer Stützrippe mit einer beispielhaften hybriden Nachlaufauschmischung,
- Figur 7
- eine rückwärtige Darstellung einer Stützrippe mit einer weiteren beispielhaften hybriden Nachlaufauschmischung,
- Figur 8
- einen Querschnitt durch eine Stützrippe mit einer seitlichen Ausblasöffnung als aktive Nachlaufauschmischung,
- Figur 9
- eine axiale Schnittansicht und eine teilweise Abwicklung eines weiteren beispielhaften Übergangskanals, und
Figur 10- eine Abwicklung eines weiteren Ausführungsbeispiels des Übergangskanals,
- FIG. 1
- an axial sectional view and a partial development of a transition channel according to an embodiment of the invention,
- FIG. 2
- FIG. 2 is a perspective view of a support rib with an exemplary trailing edge-side passive lag replacement mixture, FIG.
- FIG. 3
- FIG. 2 is a side view of a support rib with another exemplary trailing edge passive follow-up compound mixing; FIG.
- FIG. 4
- a rear view of a support rib with an exemplary active Nachlaufauschmischung,
- FIG. 5
- a rear view of a support rib with another exemplary active Nachlaufauschmischung,
- FIG. 6
- a rear view of a support rib with an exemplary hybrid lag exchange mixture,
- FIG. 7
- a rear view of a support rib with another exemplary hybrid lag exchange mixture,
- FIG. 8
- a cross section through a support rib with a side exhaust opening as an active Nachlaufauschmischung,
- FIG. 9
- an axial sectional view and a partial development of another exemplary transition channel, and
- FIG. 10
- a development of a further embodiment of the transition channel,
In den Figuren tragen gleiche konstruktive Elemente das gleiche Bezugszeichen, wobei bei mehreren gleichen Elementen in einer Figur aus Gründen der Übersicht lediglich ein Element mit einem Bezugszeichen versehen ist bzw. sein kann.In the figures, the same structural elements bear the same reference numerals, with several identical elements in a figure for reasons of clarity, only one element is provided with a reference numeral or may be.
In
Der Übergangskanal 1 ist in einem Turbinengehäuse feststehend gelagert, wohingegen die Hochdruckturbine 2 und die Niederdruckturbine 4 jeweils Laufschaufelreihe 6 aufweisen, die um eine Drehachse bzw. Turbinenachse R in Rotationsrichtung U rotieren. Der Übergangskanal 1 umgreift die Drehachse R und hat einen ringförmigen Strömungsquerschnitt. Er hat eine radial innere Kanalwandung 8, eine radial äußere Kanalwandung 10 sowie eine hochdruckturbinenseitige Eintrittsfläche F1 und eine niederdruckturbinenseitige Austrittsfläche F2. Wie in der
Es hat sich als vorteilhaft gezeigt, wenn ein axiales Flächenverhältnis Austrittsfläche F2 zu Eintrittsfläche F1 zwischen 2 und 5 liegt (2 ≤ F2 / F1 ≤ 5) und/oder ein Strömungsablenkungswinkel Δα = α1 - α2 weniger als 50° beträgt. Wie in
Der Übergangskanal 1 weist zur Versteifung eine Vielzahl von Stützrippen 14 auf, die sich zwischen der inneren Kanalwandung 8 und der äußeren Kanalwandung 10 erstrecken und die in Umfangsrichtung betrachtet gleichmäßig in dem Übergangskanal 1 verteilt sind. Die Stützrippen 14 weisen eine vergleichsweise große relative Dicke auf, um ihre Stützwirkung erfüllen und nicht skizzierte Versorgungsleitungen aufnehmen zu können. Zudem haben sie ein tragflächenartiges Profil zum Umlenken der Strömung 12 in Umfangsrichtung bzw. Rotationsrichtung. Im Bereich ihrer jeweiligen Hinterkante 16 haben sie eine durch einen Kreis angedeutete Nachlaufausmischung 18 in Form einer passiven Nachlaufausmischung 20, (
Eine in
Eine in
In
In
In
In
In
Wie in den
Wie im oberen Bereich der
In
In weiteren beispielhaften Abwandlungen können jeweils bis zu fünf Splitterschaufeln 42 zwischen zwei Stützrippen 14 angeordnet sein. Gegebenenfalls sind auch mehr als fünf Splitterschaufeln 42 zwischen zwei Stützrippen 14 angeordnet.In further exemplary modifications, in each case up to five
Zudem sind in
Zusammengefasst können miteinander kombinierbare Merkmale der Stützrippen 14 mit den Splitterschaufeln 42 wie folgt angegeben werden:
- a) In dem Übergangskanal sind umlenkende Stützrippen 14 und dünne Splitterschaufeln 42 in Tandembauweise angeordnet;
- b) die relative Dicke dmax, Splitter / L der Splitterschaufeln 42 ist kleiner als ein Grenzwert
dmax, Splitter / L < 15 %; insbesondere dmax, Splitter / L <10 %; - c) die axiale Bautiefe der Splitterschaufeln 42 beträgt
25 % < Lax, Splitter / Lax, TMTF; insbesondere 30 % < Lax, Splitter / Lax, TMTF; und/oder
Lax, Splitter / Lax, TMTF <100 %; - d) die Splitterschaufeln 42 erstrecken sich in einem Bereich, der in axialer Richtung frühestens bei 30 % Lax, TMTF beginnt und bei höchstens 125 % Lax, TMTF endet. Somit sind die
Splitterschaufeln 42gegenüber Vorderkanten 46der Stützrippen 14 in Strömungsrichtung nach hinten versetzt und können Hinterkanten 16der Stützrippen 14 nach hinten überragen.
- a) In the transition channel deflecting
support ribs 14 andthin splitter blades 42 are arranged in tandem construction; - b) the relative thickness d max, splitter / L of the
splitter blades 42 is smaller than a limit value
d max , splitter / L <15%; in particular d max , splitter / L <10%; - c) the axial depth of the
splitter blades 42 is
25% <L ax, splitter / L ax, TMTF ; in particular 30% <L ax, splitter / L ax, TMTF ; and or
L ax, splitter / L ax, TMTF <100%; - d) the
fragmentation blades 42 extend in a region which begins at the earliest in the axial direction at 30% L ax , TMTF and ends at at most 125% L ax, TMTF . Thus, thesplitter blades 42 are offset from the leadingedges 46 of thesupport ribs 14 in the flow direction to the rear and can project beyond trailingedges 16 of thesupport ribs 14 to the rear.
Es hat sich als vorteilhaft erwiesen, wenn bei einer Splitterschaufel 42 die Teilungen T1 und T2, bei mehreren Splitterschaufeln 42a, etc. die Teilungen T1 bis Tn (bei n - 1 Splitterschaufeln) unterschiedlich sind. Die Splittersehnenlängen LSplitter können dann auch unterschiedlich sein.It has proved to be advantageous if, in the case of a
Offenbart sind ein Übergangskanal für eine Strömungsmaschine, insbesondere ein Flugzeugtriebwerk, zum Bilden eines Strömungskanals zwischen einem stromaufwärtigen Strömungsquerschnitt und einem stromabwärtigen Strömungsquerschnitt, mit Stützrippen, die sich zwischen einer radial inneren Kanalwandung und einer radial äußeren Kanalwandung erstrecken und jeweils ein Profil zur Umlenkung einer Strömung von einer Eintrittsfläche zu einer Austrittsfläche des Übergangskanals aufweisen, wobei die Stützrippen jeweils im Bereich ihrer Hinterkante eine Profilvariation und/oder zumindest eine Ausblasöffnung zum Ausblasen eines Fluids aufweisen, sowie eine Strömungsmaschine mit einem derartigen Übergangskanal.Disclosed are a transitional channel for a turbomachine, in particular an aircraft engine, for forming a flow channel between an upstream flow cross-section and a downstream flow cross-section, with support ribs extending between a radially inner channel wall and a radially outer channel wall and a profile for deflecting a flow of an inlet surface to an outlet surface of the transition channel, wherein the support ribs each have a profile variation and / or at least one exhaust opening for blowing out a fluid in the region of its trailing edge, as well as a turbomachine with such a transitional channel.
- 11
- ÜbergangskanalTransition duct
- 22
- HochdruckturbineHigh-pressure turbine
- 44
- Niederdruckturbine von derLow pressure turbine of the
- 66
- Laufschaufelblade
- 88th
- innere Kanalwandunginner channel wall
- 1010
- äußere Kanalwandungouter channel wall
- 1212
- Strömungflow
- 1414
- Stützrippesupporting rib
- 1616
- Hinterkantetrailing edge
- 1818
- NachlaufausmischungNachlaufausmischung
- 2020
- Profilvariationprofile variation
- 2222
- Ausblasöffnungexhaust vent
- 2424
- Saugseitesuction
- 2626
- Druckseitepressure side
- 2727
- Hilfslinieledger line
- 2828
- SaugseitenabschnittSaugseitenabschnitt
- 3030
- DruckseitenabschnittPressure side portion
- 3232
- saugseitige Schlitzflächesuction slot surface
- 3434
- druckseitige Schlitzflächepressure-side slot surface
- 3636
- saugseitige Abströmflächesuction-side outflow surface
- 3838
- druckseitige Abströmflächepressure-side outflow surface
- 4040
- SaugseitenabschnittSaugseitenabschnitt
- 42, 42a, b42, 42a, b
- Strömungsteilerschaufel / SplitterschaufelFlow splitter scoop / splinter scoop
- 4444
- Sekundärströmungsecondary flow
- 4646
- Vorderkanteleading edge
- α1 α 1
- Strömungswinkel EintrittsströmungFlow angle inlet flow
- α1 α 1
- Strömungswinkel AustrittsströmungFlow angle outlet flow
- ΔαΔα
- StrömungsablenkungswinkelFlow deflection angle
- dmax d max
- Größte Profildicke der StützrippenLargest profile thickness of the supporting ribs
- dmax,Splitter d max, splinters
- Größte Profildicke der SplitterschaufelnLargest profile thickness of the splitter blades
- F1 F 1
- Eintrittsfläche am Anfang des ÜbergangkanalsEntrance surface at the beginning of the transitional channel
- F2 F 2
- Austrittsfläche am Ende des ÜbergangkanalsExit surface at the end of the transition channel
- LL
- Profilsehnenlänge der StützrippenProfile chord length of support ribs
- LSplitter L splitter
- Profilsehnenlänge der SplitterschaufelnProfile chord length of splinter blades
- Lax L ax
- Axiale Bautiefe der StützrippenAxial depth of support ribs
- Lax,Splitter L ax, splinters
- Axiale Bautiefe der SplitterschaufelnAxial depth of fragmentation blades
- Lax,TMTF L ax, TMTF
- Axiale Bautiefe des ÜbergangskanalsAxial depth of the transition channel
- RR
- Drehachse / TurbinenachseRotary axis / turbine axis
- T1 bis n T 1 to n
- Teilung (Abstand senkrecht zur Drehachse verlaufend) zwischen den Austrittskanten der Stützrippen und der Splitterschaufel)Pitch (distance perpendicular to the axis of rotation) between the exit edges of the support ribs and the splitter blade)
- UU
- Rotationsrichtungdirection of rotation
Claims (12)
- Transition duct (1) for a turbomachine, in particular an aircraft engine, for forming a flow duct between a high-pressure turbine and a low-pressure turbine between an upstream flow cross section and a downstream flow cross section, comprising support ribs (14) which extend between a radially inner duct wall (8) and a radially outer duct wall (10) and which comprise in each case a profiled region for deflecting a flow from an inlet surface (F1) to an outlet surface (F2) of the transition duct (1), characterized in that the support ribs (14) each comprise, in the region of the trailing edge thereof (16), a profile variation (20) for passive wake-mixing, and at least one blow-out opening (22) for blowing out a fluid for active wake-mixing, and a cooling stage of the support ribs (14) in the region of the trailing edges thereof.
- Transition duct according to claim 1, wherein the trailing edge (16) is alternately offset with respect to the suction side (24) and the pressure side (26).
- Transition duct according to claim 1, wherein the trailing edge (16) is designed so as to be undulating in the flow direction.
- Transition duct according to claim 1, wherein the at least one blow-out opening (22) emerges from the trailing edge (16) between a suction side (24) and the pressure side (26).
- Transition duct according to claim 4, wherein the at least one blow-out opening (22) is designed as a longitudinal slot which extends from the inner duct wall (8) to the outer duct wall (10), and wherein a suction-side slot face (32) is undulating and a pressure-side slot face (34), located opposite, is designed so as to be without variation.
- Transition duct according to either claim 4 or claim 5, wherein a suction-side outflow face (36), which is located opposite the suction-side slot face (32), is designed so as to be undulating.
- Transition duct according to claim 4, wherein the at least one blow-out opening (22) is designed as a longitudinal slot and a pressure-side slot face (34) is designed so as to be undulating and a suction-side slot face (32), located opposite, is designed so as to be without variation.
- Transition duct according to either claim 4 or claim 7, wherein a pressure-side outflow face (38), which is located opposite the pressure-side slot face (34), is designed so as to be undulating.
- Transition duct according to claim 1, wherein the blow-out opening (22) emerges on the suction side.
- Transition duct according to any of the preceding claims, wherein flow-splitter blades (42) are arranged between the support ribs (14) and have a lower relative profile thickness (dmax,Splitter/L) than the support ribs (14).
- Transition duct according to claim 10, wherein the flow-splitter blades (42) are provided with a trailing-edge-side profile variation (20) and/or with at least one blow-out opening (22).
- Turbomachine comprising a transition duct (1) according to any of the preceding claims.
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES12170498T ES2746966T3 (en) | 2012-06-01 | 2012-06-01 | Transition channel for a turbomachine and turbomachine |
EP12170498.5A EP2669474B1 (en) | 2012-06-01 | 2012-06-01 | Transition channel for a fluid flow engine and fluid flow engine |
US13/904,787 US20130330180A1 (en) | 2012-06-01 | 2013-05-29 | Passage channel for a turbomachine and turbomachine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
EP12170498.5A EP2669474B1 (en) | 2012-06-01 | 2012-06-01 | Transition channel for a fluid flow engine and fluid flow engine |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2669474A1 EP2669474A1 (en) | 2013-12-04 |
EP2669474B1 true EP2669474B1 (en) | 2019-08-07 |
Family
ID=46318883
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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EP12170498.5A Active EP2669474B1 (en) | 2012-06-01 | 2012-06-01 | Transition channel for a fluid flow engine and fluid flow engine |
Country Status (3)
Country | Link |
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US (1) | US20130330180A1 (en) |
EP (1) | EP2669474B1 (en) |
ES (1) | ES2746966T3 (en) |
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KR101799071B1 (en) * | 2016-01-22 | 2017-11-17 | 인하대학교 산학협력단 | Stator splitter blades with single-stage transonic axial compressor |
CN105673097B (en) * | 2016-04-15 | 2017-08-29 | 中国科学院工程热物理研究所 | Transition section structure and its design method between a kind of low degree of admission partial-air admission stage of turbine |
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Also Published As
Publication number | Publication date |
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EP2669474A1 (en) | 2013-12-04 |
ES2746966T3 (en) | 2020-03-09 |
US20130330180A1 (en) | 2013-12-12 |
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